2018 AAS/AIAA Astrodynamics Specialist Conference August 19-23 Snowbird, UT - Space Flight ...
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2018 AAS/AIAA Astrodynamics
Specialist Conference
August 19-23
Snowbird, UT
AAS General Chair AIAA General Chair
Dr. Belinda Marchand Dr. Brandon A. Jones
Progalaxia, LLC The University of Texas at Austin
AAS Technical Chair AIAA Technical Chair
Dr. Puneet Singla Dr. Ryan Weisman
The Pennsylvania State University Air Force Research Laboratory
08/19/2018
2018 AAS/AIAA ASTRODYNAMICS SPECIALIST CONFERENCE
CONFERENCE INFORMATION
GENERAL INFORMATION
Welcome to the 2018 Astrodynamics Specialist Conference, hosted by the American Astronautical Society
(AAS) and co-hosted by the American Institute of Aeronautics and Astronautics (AIAA), August 19 – 23, 2018.
This meeting is organized by the AAS Space Flight Mechanics Committee and the AIAA Astrodynamics
Technical Committee, and held at The Cliff Lodge, 9320 Cliff Lodge Dr., Snowbird, UT 84092, (801)-933-
2222, https://www.snowbird.com/lodging/the-cliff-lodge/.
REGISTRATION
Registration Site (https://www.xcdsystem.com/aas/attendee/index.cfm?ID=cQgRz2U)
In order to encourage early registration, we have implemented the following conference registration rate
structure: Register by June 30, 2018 and save $70!
Category Early Registration Registration Walk-up Registration
(through Jun 30, 2018) (beginning Jul 1, 2018) (beginning Jul 26, 2018)
Full - AAS or AIAA $590 $660 $760
Member
Full - Non-member $690 $695 $795
Retired (Member) or $200 $270 $370
Student*
Retired - Non-member $300 $370 $470
*does not include proceedings CD
Refunds will be issued in full until July 24, 2018. A 10% fee will be assessed for all refunds issued after that
date and until 8:00 am PST August 18, 2018. No refunds will be issued after 8:00 am PST August 18, 2018.
One ticket to The Summit at Snowbird on Tuesday evening is included with every registration. This includes
dinner at the top of the mountain and the tram. Guest tickets for the event may be purchased for $70 per person.
More information about the offsite event is included below.
All registrants and guests are invited to the welcome reception on Sunday evening for food and drinks.
A conference registration and check-in table will be located in the Front Desk Lobby of the Cliff Lodge and
will be staffed according to the following schedule:
Ø Sunday August 19: 3pm – 6pm
Ø Monday August 20: 7:30am – 2pm
Ø Tuesday August 21: 8am – 2pm
Ø Wednesday August 22: 8am – 2pm
Ø Thursday August 23: 8am – 10 am
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We will accept registration and payment on-site for those who have not pre-registered online, but we strongly recommend online registration before the conference in order to avoid delays (see URL above). Pre-registration also gives you free access to pre-print technical papers. On-site payment by credit card will be only through the AAS website using a computer at the registration table. Any checks should be made payable to the “American Astronautical Society.” Credit: Cover image of the GRACE Follow-On mission is courtesy of NASA. Page 2 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT
SCHEDULE OF EVENTS
Technical sessions begin on Monday, 20 August, at 8 am. The last technical sessions end at 12:20 pm on
Thursday, 23 August. Presentations are limited to 15 minutes with an additional 5 minutes for questions and
answers. Each session has a 20-minute morning or afternoon break. Authors are required to be in their session
room 30 minutes prior to the start of their sessions. No speakers’ breakfast will be served.
Day Start End Function Room
3pm 6pm Registration Front Desk
Lobby
19 August
Sunday
6pm 9pm Early Bird Reception (Food and Hosted Bar) Conference
Center Terrace
7:30am 2pm Registration Front Desk
Lobby
8am 12pm Session 1: Astrodynamics I Superior A
8am 12pm Session 2: Prox. Missions and Formation Flying I Superior B
8am 12pm Session 3: Trajectory Design and Opt. I Maybird
8am 12pm Session 4: Space Situational Awareness I Cirque
9:40am 10:00am Morning Break Superior Lobby
Noon 1:30pm Joint Technical Committee Lunch Aerie Private
20 August
Dining Room
Monday
1:30pm 5:30pm Session 5: Attitude Dynamics & Control I Superior B
1:30pm 5:30pm Session 6: Spacecraft GNC I Superior A
1:30pm 5:30pm Session 7: Asteroid & Non-Earth Orb. Missions I Maybird
1:30pm 5:30pm Session 8: Orbital Debris Cirque
3:10pm 3:30pm Afternoon Break Superior Lobby
5:30pm 6:30pm Cocktail Reception Conference
Center Terrace
6:30pm 8:30pm Dirk Brouwer Award Plenary and Breakwell Ballroom 1
Student Travel Award Presentation
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Day Start End Function Room
8am 2pm Registration Lobby
8am 12pm Session 9: Astrodynamics II Superior A
8am 12pm Session 10: Trajectory Design and Optimization II Maybird
8am 12pm Session 11: Attitude Dynamics & Control II Superior B
8am 12pm Session 12: Space Situational Awareness II Cirque
9:40am 10:00am Morning Break Superior Lobby
21 August
Tuesday
Noon 1:30pm AIAA Technical Committee Lunch Aerie Private
Dining Room
1:30pm 5:30pm Session 13: Prox. Missions and Formation Flying II Superior B
1:30pm 5:30pm Session 14: Orbit Determination Superior A
1:30pm 5:30pm Session 15: Trajectory Design and Optimization III Maybird
1:30pm 5:30pm Session 16: Spacecraft GNC II Cirque
3:10pm 3:30pm Afternoon Break Superior Lobby
6pm 9pm Offsite Event: The Summit (tram to mountain top) Summit
8am 2pm Registration Front Desk
Lobby
8am 12pm Session 17: Astrodynamics III Superior A
8am 12pm Session 18: Asteroid & Non-Earth Orb. Missions II Cirque
Wednesday
22 August
8am 12pm Session 19: Trajectory Design and Optimization IV Maybird
8am 12pm Session 20: Spacecraft GNC III Superior B
9:40am 10:00am Morning Break Superior Lobby
Noon 1:30pm AAS Technical Committee Lunch Aerie Private
Dining Room
1:30pm 4:30pm Session 21: Space Situational Awareness III Cirque
Page 4 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT
Day Start End Function Room
1:30pm 4:30pm Session 22: Attitude Dynamics & Control III Superior B
1:30pm 4:30pm Session 23: Special Session – Mission Design for Maybird
Spacecraft in Near Rectilinear Halo Orbits
3:30pm 3:50pm Afternoon Break Superior Lobby
Wednesday
22 August
4:30pm 6:30pm Town Hall Meeting: Astrodynamics Research Superior A
Funding
6:00pm 7:00pm Conference Administration Subcommittee Cirque
6:00pm 7:00pm Technical Administration Subcommittee Maybird
6:00pm 7:00pm Website Administration Subcommittee Superior B
8am 12noon Registration Front Desk
Lobby
8am 12:00pm Session 24: Trajectory Design and Optimization V Maybird
23 August
Thursday
8am 12:00pm Session 25: Space Situational Awareness IV Cirque
8am 12:00pm Session 26: Astrodynamics IV Superior A
9:40am 10:00am Morning Break Superior Lobby
A map of the Cliff Lodge and the relevant meeting rooms appears on the next page.
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SPECIAL EVENTS
EARLY BIRD RECEPTION
Sunday, 19 August 6:00 – 9:00 pm
Location: Conference Center Terrace
DIRK BROUWER AWARD PLENARY AND BREAKWELL TRAVEL AWARD
PRESENTATION:
Monday, 20 August 5:30 – 6:30 pm (Awards Reception)
6:30 – 8:30 pm (Ceremony and Lecture)
Location: Conference Center Terrace (Awards Reception)
Ballroom 1 (Ceremony and Lecture)
In addition to the plenary talk and travel awards, new AAS Fellows will be honored:
• Bobby Braun
• Antonio Elipe
• Ryan Russell
• Puneet Singla
Fifty Years of Tethered Space Systems
The feasibility of using tethered systems in space was first demonstrated in September 1966 when Gemini XI
was connected by a tether to the Agena Target Vehicle. Since then many tethered space systems have flown
with various mission objectives. Tethered satellites have been proposed for scores of applications such as upper
atmospheric studies, electrodynamic propulsion, creation of artificial gravity, formation flying, debris removal,
etc. These proposals have led to many interesting problems in astrodynamics. Some of these problems will be
discussed in the talk. Some of the recent tethered satellite missions as well as the ones to be launched in the
near-term will be described.
Dirk Brouwer Award Honoree
Dr. Arun K. Misra is the Thomas Workman Professor in the Department of Mechanical
Engineering at McGill University in Montreal, Canada. His research interests lie in the
areas of dynamics and control of tethered satellites, large space structures, formation
flight and space robotics. Dr. Misra is a Fellow of the American Institute of Aeronautics
and Astronautics (AIAA) as well as of the American Astronautical Society (AAS). He
has been elected to the International Academy of Astronautics and to the Canadian
Academy of Engineering.
Page 9 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTTHE SUMMIT AT SNOWBIRD
Tuesday, 21 August 7:00 – 9:00 pm (Plated Dinner)
Location The Summit at Snowbird
The Summit is Snowbird’s newest year-round guest facility located atop Hidden Peak at 11,000 feet. Just a few
steps from the Aerial Tram, The Summit is accessible for any tram passenger whether on foot, skis, bikes or
boards.
All conference registrations will receive an event ticket, which a tram ride to and from the top of the mountain.
Tram service will begin at 5:45pm. Dinner will be served at 7pm.
Guest tickets are available for $70 each on the conference registration site and include the tram ride and dinner.
Conference attendees and guests are required to specify their selected dinner at the time of registration.
Options include:
- Herb roasted pork loin, pan juices, warm apple chutney, butternut squash, seasonal vegetables
- Breast of chicken saltimbocca), prosciutto, sage-caper sauce, orecchiette with broccoli and asiago
- Grilled vegetable kebabs, lemon tahini sauce, braised lentil, and pine nut pilaf
Be sure to bring your meal ticket (provided at registration) to the event.
Page 10 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTTRANSPORTATION TO/FROM THE SUMMIT Attendess and guests will take the Aerial Tram from the Village to The Summit. Locations may be seen on the map (page 6). Tram tickets will be available at the mountain base where you board the tram. Please note that each ticket is for a single round trip, i.e., attendees will not be able to return to The Summit after completing the return trip. For those that prefer not to walk from the hotel to the tram base, there will be a shuttle available. Details on the tram and shuttle schedule follow. Trams Start Running: 5:45pm Tram Frequency: 15 minutes Ride Duration: ~7 minutes Shuttle to Tram Base: 5:15-7pm Shuttle Duration: 5-7 minutes Shuttle Frequency: 15 minutes Dinner: 7-9:00pm Last Tram from Summit: 9:30pm Shuttle to Hotel from Tram: 8:30-10:00pm Return Shuttle Frequency: 30 minutes Conference organizers highly recommend that attendees and guests begin their trip to The Summit early. (This also provides more opportunities to enjoy the view!) Each tram car only holds 60-70 people comfortably, and there will be 250+ people attending the offsite event. There will be five (5) tram trips available from beginning of operation until the start of dinner. Page 11 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT
CONFERENCE LOCATION THE CLIFF LODGE 9320 Cliff Lodge Dr. Snowbird, UT, 84092 https://reservations.snowbird.com/ (801) 933-2222 (voice) 1-800-232-9542 (toll-free) 1-800-453-3000 or 1801-947-8220 (Central reservation office, US callers) 00 800 4400 5511 (Reservations, international) The Cliff Lodge at Snowbird is one of North America’s most iconic ski lodges. The majesty of Little Cottonwood Canyon can be explored from the views each room provides whether facing Snowbird’s ski slopes or peering down the glacially carved canyons spilling into the Salt Lake City valley below. Within walking distance to Snowbird’s pedestrian village, The Cliff Lodge offers comfortable lodging for the whole family or group. Other amenities include an exercise room, resort-wide internet service, room service, concierge and a state-licensed daycare facility. Among Snowbird's excellent selection of dining opportunities, The Aerie Restaurant and Lounge and The Atrium are open year-round and provide diverse menus for every palate. After a day on the mountain, relax at the outdoor pool or The Cliff Spa. Open year-round, a heated swimming pool and three hot tubs are located outdoors on Level 3. Located on the 9th and 10th floors, The Cliff Spa features over 30 treatment and salon services, yoga studio, fitness center, rooftop pool and hot tub. A room block with the Government Per Diem Rate ($117/night, $10 per additional person per night, $10 per room resort fee) will be held through July 18, 2018. Reservations requested after this date will be accepted Page 12 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT
based upon availability and subject to the hotel's prevailing rate. We encourage all conference attendees to
make your hotel reservation early!
Attendees may register at the personal group web page listed below or they may call the hotel (see voice number
above). Please be sure to mention the group code AAS or the group name "American Astronautical Society"
when making reservations in order to receive the group rate. Attendees may book rooms at the group rate either
on-line or over the phone. Online bookings should use the “Group Code” 2C81OG. When booking on-line,
full payment is required at time of booking. When calling in, a one-night deposit is required at the time of
booking. Either method has a 72-hour prior cancellation policy to avoid a one-night fee. Group arrival is
August 18, 2018 and Group Departure is August 23, 2018.
Group Reservation Page:
https://reservations.snowbird.com/
Cancellations must be made 72 hours in advance of intended arrival.
The required resort fee includes self-parking and internet access.
ARRIVAL INFORMATION
Check-In and Checkout
• Check-in: 4:00 PM
• Check-out: 11:00 AM
Parking
Self-parking is included in the resort fee when staying at the conference hotel.
HOTEL SERVICES AND AMENITIES
• 24-hour Front Desk
• Concierge Service (located at the front desk)
• Room Service
• Wireless high-speed Internet access in all guest suites and public areas
• Fitness center and yoga studio
• In-room coffee
• USA Today
• Business center with first 15 minutes free
• Heated swimming pool
• Hot tub
• Cliff Spa
• Luggage Storage
Page 13 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTTRANSPORTATION INFO
The greater Salt Lake City, UT area is served by the Salt Lake City International Airport (SLC). The Snowbird
Resort is located roughly 31.9 miles southeast of the Salt Lake City International Airport, approximately 41-
minutes one-way. The hotel does not offer a free shuttle to/from the hotel. However, for those not traveling via
rental vehicle, there are several at-cost transportation options available. The table below shows a cost
comparison across some of those options, though the actual pricing should be verified directly with the
appropriate vendor on the dates of travel.
Image Source: https://ride.guru/.
A mid-range alternative, in terms is cost, is available through Canyon Transportation, as noted below. This is
less expensive than a Taxi but more expensive than Uber or Lyft.
DIRECTIONS FROM AIRPORT
FROM SLC to Snowbird, UT
Take I-80 east to I-215 south. Take Exit 6 (6200 South) and go east on 6200 South, toward the mountains. This
road will lead you straight to UT-210 and up Little Cottonwood Canyon to Snowbird.
Page 14 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTUBER/LYFT
Uber and Lyft operate between Salt Lake City Airport and The Snowbird Resort. The costs range from the high
$20’s to the mid $30’s for UberX and UberXL (see https://www.uber.com/fare-estimate/) or $43 to $60 with
Lyft and Lyft Plus, (see https://www.lyft.com/fare-estimate).
CANYON TRANSPORTATION
Phone: (801) 255-1841
Website: http://canyontransport.com/
Canyon transportation, which holds an exclusive contract with Snowbird, offers a reasonably priced shared ride
service to/from the resort. Private SUV’s and vans are also available. The rates, at the time of this publication,
are posted below. A shared ride arrangement costs around $82 for a round trip, or $45 one-way. Reservations
are highly recommended, but you can also visit their desk at the airport and they will do their best to get you
to the resort in a timely fashion.
One Way Round Trip
Shared Ride
Adult $45 $82
Children – Under 12 $28 $55
Private SUV (1-4 passengers) $180 $360
Private Van (1-5 passengers) $225 $450
Private Van (6 passengers) $230 $460
Private Van (7-8 passengers) $255 $510
Private Mini Coach (1-14 passengers) $320 $640
Pricing Source: http://canyontransport.com/rates-reservations/
TAXI
Taxi service between SLC and Snowbird is available. The estimated one-way fare (at the time of publication)
is $75.
AREA ATTRACTIONS
The Cliff Lodge is located at the mountain based in Snowbird, UT. In the summer, the resort offers a variety
of activities for families (aerial tram, mountain coaster, ropes course, etc.) and more adventurous adults (vertical
drop, mountain biking). Details on these activities and more, including how to make reservations where
required, may be found at http://www.snowbird.com.
SNOWBIRD OKTOBERFEST
Snowbird is holding its annual Oktoberfest Aug. 18-Oct. 21. This event is held Sat.-Sun., 12 noon-6:30pm
every weekend during that time, and admission is free. Early arrivals may sample a variety of beers from
American pale ales to stouts made with a wide variety of hops and brew methods. This annual festival was
voted one of America’s 10 Best Oktoberfests by Men’s Journal Magazine. More details on the event may be
found at https://www.snowbird.com/oktoberfest/.
Page 15 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTSNOWBIRD CENTER The Snowbird Center, which is within walking distance of The Cliff Lodge, offers a variety of dining, nightlife, and shopping venues. A map of the center may be found at: https://www.snowbird.com/uploaded/meetings-pdfs/snowbird_villagemap.pdf ADDITIONAL INFORMATION SPEAKER ORIENTATION Authors should have submitted a brief (approximately 50 words or 3 sentences) speaker’s bio with their abstract submission. Author presentations (preferably in PDF format) will be submitted through a web-based system and are due by Friday August 17th, 2018, 23:59:59 Eastern Time. Authors are required to maintain close correspondence with your Session chair regarding the presentations of your manuscript. Please be in the session room 30 minutes prior to the start of their sessions. No speakers’ breakfast will be served. Authors are reminded that the deadline to upload pre-prints to the https://www.xcdsystem.com/aas/ website is before August 10, 2018, 23:59:59 Eastern Time. VOLUNTEERS Volunteers that would like to staff the registration table may sign up at the registration table. PRESENTATIONS Each presentation is limited to 15 minutes. An additional five minutes is allotted between presentations for audience participation and transition. Session chairs shall maintain the posted schedule to allow attendees the option of joining a parallel session. Each room is equipped with a laser pointer, an electrical outlet, and a video projector that can be driven by a computer. Presenters shall coordinate with their Session Chairs regarding the computing equipment, software, and media requirements for the session; however, each presenter is ultimately responsible for having the necessary computer and software available to drive the presentation. Microsoft PowerPoint and PDF are the most common formats. "NO-PAPER, NO-PODIUM" POLICY Completed manuscripts shall be electronically uploaded to the submission site before the conference, limited to 20 pages in length, and conform to the AAS conference paper format. If the completed manuscript is not contributed on time, it will not be presented at the conference. If there is no conference presentation by an author, the contributed manuscript shall be withdrawn. Each author also acknowledges that he or she is releasing technical information to the general public and that respective papers and presentations have been cleared for public release. If any author of a paper is a US person (citizen or permanent resident), he or she acknowledges that the release of these data and content of the paper and presentation conforms to ITAR and are not on the USML. The information contained in these documents is neither classified, SBU, FOUO, nor proprietary to any sponsoring organization. Page 16 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT
PRE-PRINTED MANUSCRIPTS
Physical copies of preprinted manuscripts are no longer available or required for the Space Flight Mechanics
Meetings or the Astrodynamics Specialist Conferences. Electronic preprints are available for download at least
72 hours before the conference at https://www.xcdsystem.com/aas/ for registrants who use the online
registration system. The hotel provides conference guests with complimentary wireless internet access in guest
rooms and the conference meeting space. Registrants without an internet-capable portable computer, or those
desiring traditional paper copies should download and print preprint manuscripts before arriving at the
conference.
CONFERENCE PROCEEDINGS
All full registrants will receive a CD of the proceedings mailed to them after the conference (extra copies are
available for $60 during the conference). However, the hardbound volume of Advances in the Astronautical
Sciences covering this conference will be available to attendees at a reduced pre-publication cost, if ordered at
the registration desk. After the conference, the hardbound proceedings will more than double in price, although
authors will still receive a special 50% discount off the post-conference rate even if they delay their order until
after the conference. Cost of Proceedings:
Ø Conference Rate $290 domestic ($380 international)
Ø Post-Conference Rate $600 (approx.)
Ø Authors (post-conference) $300 (approx.)
Although the availability of hardcopy proceedings enhances the longevity of your work and elevates the
importance of your conference contribution, please note that conference proceedings are not considered an
archival publication. Authors are encouraged to submit their manuscripts after the meeting to one of the relevant
journals, such as:
Journal of the Astronautical Sciences
Editor-in-Chief: Kathleen C. Howell
School of Aeronautics and Astronautics
3233 Armstrong Hall
Purdue University
West Lafayette, IN 47907
(765) 494-5786
howell@purdue.edu
Journal of Guidance, Control and Dynamics
Editor-in-Chief: Dr. Ping Lu, Iowa State University
Manuscripts can be submitted via: https://mc.manuscriptcentral.com/aiaa
Journal of Spacecraft and Rockets
Editor-in-Chief: Dr. Robert D. Braun, Georgia Institute of Technology
Manuscripts can be submitted via: https://mc.manuscriptcentral.com/aiaa
SATISFACTION SURVEY
Registrants are highly encouraged to record their level of satisfaction and conference preferences in an
anonymous survey taken throughout the time of the conference. Please return the survey form given to you
when you check in at the registration table to the registration table before departing from the conference.
Page 17 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTCOMMITTEE MEETINGS Committee seating is limited to committee members and invited guests. Committee and subcommittee meetings will be held according to the schedule at the beginning of the program. Page 18 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT
Conference Technical Session Schedule
Last Update: 13 August 2018
The Most Up-toDate Full Schedule at : https://www.xcdsystem.com/aas/program/tech_program.cfm
The web interface at https://www.xcdsystem.com/aas/program/OjvenM6/index.cfm
Monday August 20, 2018
Aug 20, 2018 Superior A – Astrodynamics – I
Monday Session 1 Astrodynamics - 1
Chair: Jeff Parker, Advanced Space
Co-Chair: Matthew Wilkins, Applied Defense Solutions
8:00 AAS A monotonic starter for solving the hyperbolic Kepler equation by Newton's
18- method
214 Antonio Elipe, Centro Universitario Defensa de Zaragoza; Juan I. Montijano,
Universidad de Zaragoza; Luis Randez, Universidad de Zaragoza; Manuel Calvo,
Universidad de Zaragoza
This communication deals with the iterative solution of the sine hyperbolic Kepler's
equation (SHK): F_g(S) = S - g arcsinh(S) ? L = 0. Since this function is monotonic
increasing and convex, any starter value S_0 such that F_g( S_0 ) > 0, leads to a a
Newton's sequence S_j monotic decreasing to the exact solution of SKE equation and
therefore has some advantages over non monotonic starters. Because of this, we are able to
construct a monotonic starter such that minimizes the computational cost and that
guarantees super-convergence by applying an optimal version of Newton-Kantorovich
theorem.
8:20 AAS Phobos's Rotational Dynamics
18- James Miller, Consultant; Gerald Hintz, University of Southern California
252
As Phobos orbits Mars, it is subjected to a torque that gives rise to an oscillation about the
line connecting the center of Mars with the center of Phobos. This oscillation is referred to
as libration and has an amplitude of about one degree. The source of the torque is the
variation or gradient of the gravity of Mars across Phobos. An equation is derived that
includes forced and transient terms.
8:40 AAS ANALYSIS OF THE EFFECT OF OBLATENESS IN THE CIRCULAR
18- RESTRICTED THREE BODY PROBLEM NEAR THE SECONDARY
267 BODY
Luke Bury, University of Colorado Boulder
Page 19 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTThe Circular-Restricted Three-Body Problem (CR3BP) is widely used for calculating
baseline trajectories. However, solutions obtained with the classic CR3BP are not
dynamically robust. The CR3BP makes large assumptions such as the circular motion of
bodies and point-mass gravitation. The purpose of this paper will be to refine the CR3BP
through the addition of the primary body’s oblateness (J2) and provide analysis on the
effect of this addition near the secondary body in real systems. Metrics considered include
zero-velocity curves, collinear equilibria point location, periodic orbit behavior, and
minimum necessary delta-V for landing on a secondary.
9:20 AAS An ecliptic perspective for analytical satellite theories
18- Ioannis Gkolias, Politecnico di Milano; Martin Lara; Camilla Colombo,
370 Politecnico di Milano
Traditionally, the forces in analytical theories for Earth satellite orbits are expressed in a
coordinate frame which involves the equatorial plane. However, for distant satellites, the
Moon and Sun attractions are equally important, and those forces are expressed more
conveniently in a frame associated to the ecliptic plane. In this work, we develop an
analytical satellite theory in which all the forces are expressed with respect to the ecliptic
plane. The main advantage of the method is that, after the averaging process, all time-
dependent terms disappear from the formulation yielding a model suitable for preliminary
design of frozen orbits.
9:40 Break
10:00 AAS Linear Covariance-Based Navigation and Maneuver Requirement
18- Determination Using Second-Order Cone Programming for Elliptical
374 Rendezvous Operation
Kai Jin, Utah State University; David Geller, Utah State University
A novel navigation and maneuver requirement determination approach for elliptical
rendezvous operation is developed in this paper. This approach can quickly determines the
optimal navigation and maneuver performance meeting trajectory dispersion
requirements. First,the trajectory dispersion with navigation and maneuver execution error
is modeled using linear covariance analysis theory. Using the trajectory dispersion as the
optimization constraint, the navigation and maneuver requirement determination problem
is formulated as a second-order cone programming problem and solved. In order to apply
this approach on a perturbed elliptical orbit rendezvous mission, a new state transition
matrix is calculated.Simulations show that the approach works well.
10:20 AAS On the Evolution of Orbits about Active Comets
18- Mark Moretto, University of Colorado Boulder; Jay McMahon, CCAR (Colorado
389 Center for Astrodynamics Research)
Spacecraft and large particles orbiting an active comet are perturbed by gas drag from the
coma. These gasses expand radially at about 0.5 km/s, much faster than orbital velocities
that are on the order of meters per second. The coma is not spherically symmetric.
Page 20 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTAccelerations from gas drag can be on the same order of gravity and are currently poorly
understood. We present semi-analytical solutions for the evolution of the Keplerian orbital
elements of a spacecraft orbiting a comet. Implications for trajectory design, operations,
and natural particle dynamics about the comet are shown.
10:40 AAS SEARCHING FOR ORBITS AROUND EQUILIBRIUM POINTS IN A
18- BINARY ASTEROID SYSTEM MODELED AS A MASS DIPOLE
396 Leonardo Torres, INPE; Priscilla Andressa Sousa-Silva, São Paulo State
University - UNESP; Diogo Sanchez, National Institute for Space Research -
INPE; Antonio Fernando Bertachini Prado, INPE
The objective of the present work is to search for orbits around the equilibrium points L1
and L2 of the restricted synchronous three-body problem. From the equations of motion of
a binary asteroid system, where one of the asteroids is modeled as a rotating mass dipole,
the initial conditions for the Lyapunov orbits were determined. A family of orbits was
constructed around the equilibrium points L1 and L2. It is intended next to find homoclinic
and heteroclinic orbits around this region.
11:00 AAS Bounded Motions Near Resonant Orbits in the Earth-Moon and Sun-Earth
18- Systems
404 Natasha Bosanac, University of Colorado, Boulder
Periodic and quasi-periodic trajectories in resonant orbit families contribute to an
underlying dynamical structure that governs motion within a multi-body system.
Characterization of both types of bounded motion in the circular restricted three-body
problem is useful when compiling an expanded design space for mission orbit selection
and trajectory construction. To achieve a complete representation of the quasi-periodic
orbits within resonant orbit families, a continuation strategy that can avoid tori with
frequencies near integer ratios is presented. This strategy is leveraged to compute and
characterize quasi-periodic orbits in various interior and exterior resonant orbit families in
the Sun-Earth and Earth-Moon systems.
11:20 AAS Mean Values in Elliptic Motion: Averaging the Legendre Polynomials
18- Aaron J. Rosengren, University of Arizona; Jeremy Correa, University of
426 Arizona; Daniel Scheeres, University of Colorado at Boulder
Averaging, being one of the oldest and most developed topics of investigation in celestial
mechanics, provides a particularly effective method for the approximate evaluation of the
dynamics of a system. We will present a systematic approach for computing the mean
values of any particular function encountered in elliptic motion. We will show that all
orbital averages occurring in perturbed Keplerian motion (assuming non-commensurate
orbital frequencies) reduce to averages of certain powers of the orbit radius; thereby
revealing the fundamental significance and profundity of Hansen's coefficients. This
method will be applied to averaging the Legendre expansion of various gravitational
potentials.
Page 21 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT11:40 AAS On the Solution to Every Lambert Problem
18- Ryan Russell, The University of Texas at Austin
456
The parameter and solution space for the zero- and multi-rev Lambert’s problem is
surveyed, including a close inspection of typical stress cases. The problem domain is
shown to be rectangular under the recent vercosine formulation, making the elusive initial
guess for Lambert’s problem amenable for interpolation. Smooth, two-dimensional
interpolated functions are generated over the full domain for up to 100 revolutions,
focusing on methods that reduce evaluation runtime. Resulting functions yield initial
guesses to solve Lambert’s equation, or may be used directly as low-resolution
solutions. The functions are archived and benchmarked for accuracy, speed, and memory
footprint.
Aug 20, 2018 Superior B – Proximity Missions & Formation Flying – I
Monday Session 2 Proximity Missions, & Formation Flying-I
Chair: David B. Spencer, Pennsylvania State University
Co-Chair: Waqar Zaidi, Applied Defense Solutions
8:00 AAS Demonstration of a propellantless spacecraft hopping maneuver on a planar
18- air bearing test bed
444 Andrew Bradstreet, Naval Postgraduate School; Josep Virgili-Llop, Naval
Postgraduate School; Marcello Romano, Naval Postgraduate School
During on-orbit servicing or exploration of small planetary bodies, robotic spacecraft may
need to move between locations on the surface of their target object. Hopping is a low
gravity mobility approach where a vehicle with robotic manipulators "jumps" between two
locations. The experimental demonstration of a propellantless hopping maneuver on a
planar air bearing test bed with a vehicle equipped with two robotic manipulators is
presented here. This is the first time, to the best knowledge of the authors, that this kind of
hopping maneuver has been tested on a dynamic hardware-in-the-loop test bed.
8:20 AAS Collocation of Geostationary Satellites in Wheel Cluster Formation
18- Chia-Chun Chao, The Aerospace Corporation
212
The concept of a wheel cluster formation in a single orbit plane has been demonstrated to
be cost effective in deployment and formation-keeping. This paper further demonstrates
through numerical simulations how the concept can be applied to the collocation of several
geostationary satellites. Both east/west and north/south stationkeeping with a tight control
box of +/-0.1 deg are simulated with sun-pointing constraint. Two control methods are
explored. One method assumes ground control of the sub-satellites, while the other method
employs the auto-feed-back controller with onboard GPS measurements. The number of
collocated satellites can be 10 or more depending on navigation capability.
Page 22 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT8:40 AAS Linearized Relative Orbital Motion Model About an Oblate Body Without
18- Averaging
218 Ethan Burnett, University of Arizona; Eric Butcher, University of Arizona; Andrew
J. Sinclair, Air Force Research Laboratory; Alan Lovell, Air Force Research
Laboratory
A new linearized differential equation model and solution for spacecraft relative motion
about an oblate body is obtained without averaging the perturbing acceleration, and
presented for the case of near-zero chief orbit eccentricity. The model is stand-alone and
does not require integration of the chief orbit, while the time-explicit solution depends only
on initial chief orbital elements, time since epoch and node crossing, and the deputy’s
initial conditions in the chief Hill frame. The resulting model outperforms previous models
obtained via averaging, and has a similar error to the GA-STM for zero initial chief orbit
eccentricity.
9:00 AAS Trajectory Optimization for Rendezvous with Bearing-only Tracking
18- Xiaoyu Chu, Beijing Institute of Technology; Kyle T. Alfriend, Texas A&M
223 University; Jingrui Zhang; Yao Zhang
This study focuses on an issue of trajectory optimization in spacecraft rendezvous when
using bearing-only target tracking. The observability of the spacecraft in the relative
motion is analyzed and verified. The rendezvous trajectory is generated by optimizing the
relevant parameters in the filtering process. Two optimization algorithms are presented.
The first is to minimize the trace of the filter covariance matrix, while the second is to
maximize the determinant of the Fisher information matrix (FIM). By balancing these
performance indices of observability with fuel consumption, the trajectory is optimized
with eclectically optimum performance.
9:20 AAS Methods for Passive Optical Detection and Relative Navigation for
18- Rendezvous with a Non-Cooperative Object at Mars
228 Alan Didion, NASA Jet Propulsion Laboratory; Austin Nicholas, Jet Propulsion
Laboratory/Caltech; Joseph Riedel, NASA Jet Propulsion Laboratory; Robert
Haw, NASA / Caltech JPL
Long-range passive optical detection of an orbiting inert sphere by a robotic Mars orbiter is
investigated and trades are described in terms of detectability via visible light in the
presence of orbit uncertainty, gravitational perturbations, and camera electronics noise. A
new approximate equation for signal-to-noise ratio (SNR) is developed to include most
relevant camera imperfections, diffraction, and stray light from the Mars limb as relevant
to this scenario. Using this method, a notional camera suite is designed to meet detection,
navigation, and redundancy requirements for an example mission scenario. Navigation
analysis results suggest the rendezvous is feasible with current technology.
9:40 Break
Page 23 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT10:00 AAS Algorithms for Small Satellite Formation Initialization
18- Robert LaRue, U.S. Air Force; Kirk W. Johnson, US Air Force
231
This study examines the initialization of SmallSat (small satellite) formations. Guidance
and control algorithms are developed to generate fuel-optimal formation initialization
trajectories. The maneuver solutions generated by the algorithms are assessed by a
numerical propagation using the nonlinear equations of motion with J2 and drag
perturbations. Initial conditions are chosen to simulate dispersal from a carrier vehicle.
Methods are presented for negating spacecraft relative velocity in the context of formation
initialization. The developed algorithms are used to examine a variety of scenarios and
draw conclusions about the effect of various design parameters in the context of formation
initialization.
10:20 AAS A MINIMAL PARAMETERIZATION ON SIX D.O.F. RELATIVE
18- ORBITAL MOTION PROBLEM USING DUAL LIE ALGEBRA
278 Daniel Condurache, Technical University of Iasi
This main goal of this research is the development of a new approach of minimal
parameterization to the full-body relative orbital motion problem. Using the isomorphism
between the Lie group of the rigid displacements and Lie group of the orthogonal dual
tensors, a solution of the problem is obtained. A representation theorem of the 6-DOF
relative orbital motion problem is given. Using the Euler dual vector, the higher-order
Rodrigues dual vector or Davenport-Euler dual angles the minimal dimensional
representations of this problem is obtained. The novelty of the method over existing
solutions is discussed and the main advantages are revealed.
10:40 AAS State-Dependent Riccati Equation Control for Spacecraft Formation Flying in
18- the Circular Restricted Three-Body Problem
312 Michael Tannous, University of Pisa - Department of Information
Engineering; Giovanni Franzini, University of Pisa - Department of Information
Engineering; Mario Innocenti, University of Pisa - Department of Information
Engineering
The use of the state-dependent Riccati equation (SDRE) technique for formation flying
control in the circular restricted three-body problem is investigated in this paper. First, the
relative dynamics of a leader-follower formation is described by computing the difference
between the equations of motion associated to the two spacecraft. Then, a pseudo-linear
form of the relative motion equations is identified in order to implement the SDRE control
technique. The effectiveness of the controller is proved by the high accuracy and the
limited control usage achieved during the numerical simulations, set up considering the
New Worlds Observer mission scenario.
11:00 AAS A Semi-analytical Approach to Characterize the Relative Motion in the
18- Vicinity of Phobos
326 Davide Conte, Pennsylvania State University; David B. Spencer, Pennsylvania
State University
Page 24 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTThis paper discusses a semi-analytical approach to approximate the relative motion of
spacecraft around Distant Retrograde Orbits (DROs) in the vicinity of Phobos. Numerical
analysis reveals that Mars-Phobos DROs can be represented in a moderately accurate way
using second-order Fourier series representations. Assuming that the relative distance
between spacecraft is small, the equations of motions can be simplified and written directly
using time-dependent coefficients which can then be semi-analytically solved to obtain a
representation of the relative motion. These equations exhibit a secular behavior,
accurately described by the Hill-Clohessy-Wiltshire equations, and a short-term cyclic
behavior due to the Phobos’ gravity.
11:20 AAS ARC-LENGTH SOLVER METHODOLOGY FOR RELATIVE ORBIT
18- DETERMINATION MEASUREMENT EQUATIONS
339 Brett Newman, Old Dominion Univ.; Alan Lovell, Air Force Research
Laboratory; Geoffrey Rose, NASA Langley Research Center; Duc Nguyen, Old
Dominion University
Numerical solution of an algebraic formulation of the Keplerian circular relative orbit
determination problem is investigated using iterative nonlinear arc-length solver
methodology. A series of angular measurements are coupled to an approximate analytic
relative motion solution. The resulting set of nonlinear measurement equations are solved
for six unknown deputy initial conditions. The arc-length method computes a continuous
family of solutions using an unknown continuation parameter. From this family, specific
solutions corresponding to a zero parameter value are extracted. The method avoids
concerns related to start value selection, convergence to trivial-undesired solutions,
divergence to infinite valued solutions, and numerical ill-conditioning.
11:40 AAS Real-Time Angular Velocity Estimation of Non-Cooperative Space Objects
18- Using Camera Measurements
420 Marcelino Mendes de Almeida, The University of Texas at Austin; Maruthi R.
Akella, University of Texas at Austin; Daniele Mortari, Texas A&M
University; Renato Zanetti, University of Texas at Austin
This paper presents a solution to the problem of estimating the relative angular velocity
(RAV) between a camera (onboard a chaser spacecraft) and an object in space (the target
spacecraft or celestial object) using camera measurements only. Our approach assumes no
prior knowledge of the initial characteristics of the target, making it seamlessly applicable
to different applications. Our algorithm pipeline uses SLAM to estimate the relative pose,
which is used as inputs to a Discrete Adaptive Angular Velocity Estimator (estimates the
Angular Velocity Direction) and a modified MEKF (estimates the Angular Velocity
Magnitude).
Aug 20, 2018 Maybird – Trajectory Design & Optimization – I
Monday Session 3 Trajectory Design & Optimization-I
Chair: Roby Wilson, Jet Propulsion Laboratory
Page 25 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT8:00 AAS 2018 Mars InSight Mission Design and Navigation Overview
18- Fernando Abilleira, NASA Jet Propulsion Laboratory/Caltech
251
Originally scheduled for a launch in the 2016 Earth to Mars opportunity, NASA’s Interior
Exploration using Seismic Investigations, Geodesy, and Heat Transport (InSight) mission
will launch the next lander to Mars in May-June 2018 arriving to the Red Planet in
November 2018. Derived from the Phoenix mission which successfully landed on Mars in
May 2008, the InSight Entry, Descent, and Landing system will place a lander in the
Elysium Planitia region. This paper specifies the mission and navigation requirements set
by the Project and how the final mission and navigation design satisfies those
requirements.
8:20 AAS Enhanced Station-Keeping Maneuver Control Technique for Delta-V Cost
18- Reduction in Korea Pathfinder Lunar Orbiter
246 Jae-ik Park, Korea Aerospace Research Institute; Diane Davis, a.i. solutions,
Inc.; Su-JIN Choi, Korea Aerospace Research Institute; Ryan Whitley, NASA; John
P. Carrico, Space Exploration Engineering, Inc.; Dong-Young Rew, Korea
Aerospace Research Institute; Seok-Weon Choi, Korea Aerospace Research
Institute
This paper proposes an enhanced control technique for station-keeping maneuvers to
reduce delta-V costs for the Korea Pathfinder Lunar Orbiter (KPLO). The reduction is
demonstrated by comparing the proposed technique against previous algorithms
implemented for maneuver operations of the Lunar Reconnaissance Orbiter (LRO) in USA
and KAGUYA in Japan. A scheduled circularization control technique combines the
advantageous points of the two methods to achieve a significant reduction in station-
keeping delta-V costs. Through Monte Carlo analysis, the efficacy and robustness of the
proposed method are verified, and the technique is shown to meet the operational
requirements of KPLO.
8:40 AAS MMS Extended Mission Design: Evaluation of a Lunar Gravity Assist Option
18- Trevor Williams, NASA/Goddard Space Flight Center; Dominic Godine, ai
250 Solutions, Inc.; Eric Palmer, ai Solutions, Inc.; Ishaan Patel, ai Solutions,
Inc.; Neil Ottenstein, a.i. solutions, Inc.; Luke Winternitz, NASA Goddard Space
Flight Center; Steven Petrinec, Lockheed Martin Advanced Technology Center
This paper describes maneuvers that were recently considered for a later extended mission
phase for the Magnetospheric Multiscale (MMS) mission. These are apogee-raises to set
up a lunar gravity assist, which in turn raises perigee for enhanced magnetopause science
collection. Since a lunar encounter is only achievable when the MMS apogee vector lies
approximately in the lunar orbit plane, the possible dates are mid-2021 or early 2027. This
study was made feasible by the fact that MMS is consuming fuel for formation
maintenance far slower than expected pre-flight, and completed the prime mission with a
significant amount of fuel remaining.
Page 26 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT9:20 AAS Evaluation of Optimal Control Algorithms Used in Spacecraft Maneuver
18- Planning
259 Chris Lawler, The US Naval Research Laboratory
Because of the nonlinearity present in the equations of motion for practical satellite orbit
dynamics, optimal control is essential in determining an appropriate maneuver sequence to
correctly change a satellite’s state above the Earth. A maneuver planning and analysis
toolkit is currently under development at the US Naval Research Laboratory that will
streamline calculation of maneuver sequences that satisfy specific mission goals. The
optimal control algorithm used in this toolkit, the E04UFF algorithm provided by the
Numerical Algorithms Group will be compared with AGI Astrogator's differential
corrector to verify this toolkit's effectiveness in solving spacecraft maneuver planning
problems.
9:40 Break
10:00 AAS TRAJECTORY ANALYSIS OF A SPACECRAFT MAKING A THREE-
18- DIMENSIONAL POWERED SWING-BY MANEUVER
262 Alessandra Ferreira, Universidade Estadual Paulista - UNESP; Rodolpho Moraes,
UNIFESP; Antonio Fernando Bertachini Prado, INPE; Othon Winter,
Universidade Estadual Paulista -UNESP
This paper proposes to study orbital maneuvers performed by the passage of a spacecraft
near of a celestial body with impulsive propulsion, considering the movement of the space
vehicle in the three-dimensional space, thus allowing the orbital plane change. This type of
maneuver can send the probe to a point far from the orbit or to cause the capture or escape
of the spacecraft by the celestial body. The effects of the orbit change on the energy and
angular momentum of the spacecraft will be presented, as well as the types of orbits and
inclination resulting from this change.
10:20 AAS Arcus Mission Design: Stable Lunar-Resonant High Earth Orbit for X-Ray
18- Astronomy
271 Laura Plice, Metis Technology Solutions; Andres Dono Perez; Lisa Policastri,
Space Exploration Engineering (SEE); John P. Carrico, Space Exploration
Engineering, Inc.; Michel Loucks, Space Exploration Engineering (SEE)
The Arcus mission, proposed for NASA’s 2016 Astrophysics Medium Explorer (MIDEX)
announcement of opportunity, will use X-ray spectroscopy to detect previously
unaccounted quantities of normal matter in the Universe. The Arcus mission design uses
4:1 lunar resonance to provide a stable orbit for visibility of widely-dispersed targets, in a
low background radiation environment, above the Van Allen belts for the minimum two-
year science mission. Additional advantages of 4:1 resonance are long term stability
without maintenance maneuvers, eclipses under 4.5 hrs, perigee radius approx. 12 Re for
data download, and streamlined operational cadence with approx. 1 week orbit period.
Page 27 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT10:40 AAS Optimal trajectories for a dual-spacecraft outer planet mission
18- Hongwei Yang, Nanjing University of Aeronautics and Astronautics; Wei You,
276 Shanghai Institute of Satellite Engineering; Shuang Li, Nanjing University of
Aeronautics and Astronautics; Xiuqiang Jiang, Nanjing University of Aeronautics
and Astronautics
A hypothetical future dual-spacecraft mission for visiting Jupiter and Uranus is considered
in this paper. The constrained impulsive trajectory optimization method using the particle
swarm optimization algorithm is proposed for the design trajectory of the mission. In
trajectory optimization, Venus-Earth-Earth-Jupiter gravity assists are employed. For low-
thrust case, an indirect method is employed for trajectory optimization based on the
impulsive-thrust trajectories. A technique for solving hybrid-thrust trajectories is also
presented. Analyses on the mission fuel consumption are conducted based on optimized
trajectories. The obtained results are expected to provide reference for future missions.
11:00 AAS Mission Analysis for an ESA contribution to the Mars Sample Return
18- campaign
277 Eric Joffre, Airbus Defence and Space Ltd; Uwe Derz, Airbus Defence and Space
Ltd; Marie-Claire Perkinson, Airbus Defence and Space Ltd; Jakob Huesing,
ESA; Friederike Beyer, ESA; Jose Manuel Sanchez Perez, ESA
Bi-lateral discussions between NASA and the European Space Agency identified the
orbiter element as a promising European-led contribution to a future international Mars
Sample Return campaign. Airbus recently completed the Mars Sample Return Architecture
Assessment Study on behalf of ESA, with the objective to identify and quantify candidate
mission architectures. The paper will describe the mission analysis that was conducted to
support preliminary system design, launch mass estimation and mission timeline for the
architectures investigated. It includes the extensive optimisation of interplanetary transfers
(with Chemical and Electric Propulsion), Mars operations including aerobraking and
rendezvous, up to Earth re-entry conditions.
11:20 AAS A Convex Optimization Approach to Mars Entry Trajectory Updating
18- Connor Noyes, University of California, Irvine; Kenneth Mease, University of
269 California, Irvine
A trajectory updating scheme is proposed for Mars entry guidance. The trajectory
generation problem is posed as an optimal control problem. The problem is convexified
and solved using convex optimization. Unlike previous convex approaches to entry
guidance, there is no iteration required and only a single optimization problem is solved.
The trajectory may be updated at fixed intervals or when the predicted final state does not
match the target state. The update scheme is applicable in reference trajectory tracking
guidance algorithms as well as in the role of predictor-corrector guidance. The
effectiveness of the method is demonstrated via numerical simulation.
11:40 AAS TRACKING CONTROL OF SPACECRAFT ATTITUDE AND POSITION
18- ON TIME DEPENDENT TRAJECTORIES USING DUAL QUATERNIONS
349
Page 28 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UTAli Tevfik Büyükkoçak, Middle East Technical University; Ozan Tekinalp, METU
Aerospace Engineering Dept.
Spacecraft attitude and position control algorithm which uses dual quaternions for
parametrization is proposed. Error dual quaternion and its derivative are obtained from the
desired attitude and position which are the trajectories of time dependent functions. This
position and orientation (pose) formulation is used with a Lyapunov based feedback
control law that includes derivative of desired attitude and position. Simulation results
show that desired attitude and position trajectories are tracked successfully by the new
algorithm.
Aug 20, 2018 Cirque – Space Situational Awareness – I
Monday Session 4 Space Situational Awareness-I
Chair: Christopher Roscoe, Applied Defense Solutions
Co-Chair: Kyle DeMars, Missouri University of Science and Technology
8:00 AAS Accurate and Efficient Collision Probability for Nonlinear Covariance
18- William Todd Cerven, Aerospace Corporation; Felix Hoots, Aerospace
213 Corporation
The location of a satellite in space is typically described by an element set or state vector at
some epoch and the location uncertainty is described by a covariance. The probability
density function is usually assumed to be Gaussian. Nonlinearities can introduce
significant errors in the propagation of the covariance and have been a topic of several
recent papers. We have developed a method to remove most of the nonlinearities and
provide accurate propagation of the uncertainty estimate for 30 days or more. This paper
demonstrates how the resulting covariance can be used to compute an accurate probability
of collision.
8:20 AAS Dynamic Sensor Steering for Target Search for Space Situational Awareness
18- Mihir Patel, University of Illinois at Urbana-Champaign; Andrew J. Sinclair, Air
355 Force Research Laboratory; Hoong Yeong, University of Illinois; Ryne Beeson,
University of Illinois at Urbana-Champaign; Koki Ho, University of Illinois,
Urbana-Champaign
This paper will develop a method for efficient sensor steering planning to search and detect
an orbiting space objects in an highly uncertain or unknown orbit using an imperfect
sensor. This problem is important for orbital sensors to perform follow-up observations of
an uncorrelated track (UCT). This paper will address this important literature gap
by creating a particle-based estimation methodology with clustering strategies to make the
search process more efficient. The resulting methods will be integrated into existing
information theoretic search strategies and the performance will be evaluated by
simulations.
Page 29 2018 AAS/AIAA Astrodynamics Specialist Conference, Snowbird, UT8:40 AAS Analysis And Design Of Collision Avoidance Maneuvers For Passive De-
18- Orbiting Missions
357 Juan Luis Gonzalo, Politecnico di Milano; Camilla Colombo, Politecnico di
Milano; Pierluigi Di Lizia, Politecnico di Milano
Collision avoidance maneuvers (CAMs) for passive de-orbiting missions using sails are
studied, maneuvering either the sail or the incoming object. Analytical and semi-analytical
expressions for the CAM are obtained leveraging the proximal motion equations,
maximizing either the total or b-plane contained deviation. When the sail performs the
CAM, different attitude-related strategies are investigated. The required amount of
propellant or sail maneuverability as function of the lead time is traded-off. Finally,
representative test cases are proposed based on data from ESA’s MASTER tool, and the
evolution of the covariance matrix with the lead time is investigated.
9:00 AAS Physically-Constrained Inverse Optimal Control for Satellite Maneuver
18- Detection
377 Richard Linares, University of Minnesota; JOSEPH RAQUEPAS, Air Force
Research Laboratory
This paper develops an approach to determine the behavior of Space Objects (SOs) using
Inverse Reinforcement Learning (IRL) and Inverse Optimal Control (IOC) theory. The
proposed approach determines the reward function that each SO is using for control
utilizing both IRL and IOC theory, thereby determining the behavior of the SOs. The
approach discussed in this work can be used to analyze maneuvering SOs from
observational data. The contribution of this work is to formulate the IRL problem using
IOC theory. The IRL problem is solved using the Pontryagin's minimum principle.
9:20 AAS Early trajectory estimate of proximate objects with an optical fence
18- Liam Healy, Naval Research Laboratory; Scott Kindl, Naval Research
381 Laboratory; Christopher Binz, Naval Research Laboratory; Christoph Englert,
NRL; Andrew Nicholas, Naval Research Laboratory
A on-board optical ``fence'' that provides angles-only relative orbital knowledge of objects
in its vicinity can be used to make early estimates of the relative orbit. A relative orbit can
be estimated from three or more observations except for the scale. Observable relative
motion is described by just three parameters instead of the full six; estimating a smaller
number of parameters gives better estimates. The most interesting is the relative drift rate,
as this determines how long the objects stay close. The estimated uncertainties for each
parameter and their variation with different orientation of the fence is studied.
9:40 Break
10:00 AAS A Direct Light Curve Inversion Scheme for Artificial Objects
18- Siwei Fan, Purdue University; Carolin Frueh, Purdue University
441
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